Abstract: The invention relates to an arrangement, in a pod of an aircraft propulsion assembly, for drawing in air and trapping foreign bodies. Said arrangement includes a main air inlet duct (11) separating into, on one hand, a channel (13) for leading air to a compressor and, on the other hand, a bypass channel (12) capable of trapping foreign bodies (5) that enter said main duct (11). Said arrangement comprises a heat exchanger (6) that extends along a section of the bypass channel (12). Said heat exchanger (6) carries out surface heat exchange along said section and is coupled with an external oil system in order to cool the oil thereof by heat exchange with the air (4) flowing in the bypass channel (12). Said bypass channel (12) has an air outlet (12a) acting as a means for discharging the foreign bodies (5).

Abstract: A turbine engine nozzle having confluent streams, the nozzle including a core cowl arranged around an annular central body and co-operating therewith to define a core annular channel for passing a flow of a core stream, the core stream on entry into the nozzle possessing an azimuth component driving residual gyratory movement of the core stream in two opposite gyratory flow directions corresponding to two operating speeds of the engine, the core cowl having an annular upstream portion that is extended downstream by an annular terminal portion having longitudinal cuts forming a plurality of flaps that overlap radially in pairs via their respective side edges in such a manner that, for each flap, one of the two side edges of the flap is positioned internally relative to the corresponding side edge of one of the adjacent flaps, while the other side edge of the flap is positioned externally relative to the corresponding side edge of the other adjacent flap.

Abstract: The invention relates to an arrangement, in a pod of an aircraft propulsion assembly, for drawing in air and trapping foreign bodies. Said arrangement includes a main air inlet duct (11) separating into, on one hand, a channel (13) for leading air to a compressor and, on the other hand, a bypass channel (12) capable of trapping foreign bodies (5) that enter said main duct (11). Said arrangement comprises a heat exchanger (6) that extends along a section of the bypass channel (12). Said heat exchanger (6) carries out surface heat exchange along said section and is coupled with an external oil system in order to cool the oil thereof by heat exchange with the air (4) flowing in the bypass channel (12). Said bypass channel (12) has an air outlet (12a) acting as a means for discharging the foreign bodies (5).

Abstract: An exhaust centerbody for a turbine engine is provided. The centerbody includes a truncated downstream part, which is connected to an upstream part by an annular ridge marking a discontinuity between the outer surfaces of the upstream and downstream parts. The outer surface of the downstream part has a substantially conical general shape, of which the tip is oriented downstream and is positioned in the region of the axis A, the axial half-section of this outer surface defining a line of which the upstream end part is substantially tangential to a straight line passing through the ridge and forming a non-zero angle ? with a tangent to the outer surface of the upstream part, in the region of the ridge, and of which the downstream end part is substantially tangential to a straight line passing through the tip and forming a non-zero angle ? with the axis A.

Abstract: A method of mixing in a discharge conduit, in a turbine engine with two or more flows, of a primary flow and a secondary flow, the two flows emerging in the discharge conduit by two coaxial ducts, separated by an internal housing which has an end downstream relative to the flow direction of the flows, the two coaxial ducts each being defined between an internal wall and an external wall, upstream of the downstream end of the internal housing, and the secondary flow surrounding the primary flow, is provided. The method includes disposing a divergent radial deflection device in the primary duct, spaced apart from the walls of the primary duct. A turbine engine including the deflection device is also provided.

Abstract: A turbine engine nozzle having confluent streams, the nozzle including a core cowl arranged around an annular central body and co-operating therewith to define a core annular channel for passing a flow of a core stream, the core stream on entry into the nozzle possessing an azimuth component driving residual gyratory movement of the core stream in two opposite gyratory flow directions corresponding to two operating speeds of the engine, the core cowl having an annular upstream portion that is extended downstream by an annular terminal portion having longitudinal cuts forming a plurality of flaps that overlap radially in pairs via their respective side edges in such a manner that, for each flap, one of the two side edges of the flap is positioned internally relative to the corresponding side edge of one of the adjacent flaps, while the other side edge of the flap is positioned externally relative to the corresponding side edge of the other adjacent flap.

Abstract: Exhaust centerbody (12?) for a turbine engine, comprising a truncated downstream part (26), which is connected to an upstream part (24) by an annular ridge (22) marking a discontinuity between the outer surfaces of the upstream and downstream parts, the outer surface of the downstream part having a substantially conical general shape, of which the tip (29) is oriented downstream and is positioned in the region of the axis A, the axial half-section of this outer surface defining a line of which the upstream end part is substantially tangential to a straight line (28) passing through the above-mentioned ridge and forming a non-zero angle ? with a tangent (30) to the outer surface of the upstream part, in the region of the ridge, and of which the downstream end part is substantially tangential to a straight line (32) passing through the above-mentioned tip and forming a non-zero angle ? with the axis A.

Abstract: A pylon configured to secure a turbine engine to a structural element of an aircraft, the pylon including a streamlined profile defined by two opposite faces and extending longitudinally between a leading edge and a trailing edge, and at least a first one of the two faces presenting at least locally a succession of non-through hollows and of bumps.

Abstract: The invention relates to a method of mixing in a discharge conduit, in a turbine engine with two or more flows, of a primary flow and a secondary flow, the two flows emerging in said discharge conduit by two coaxial ducts, separated by an internal housing which has an end downstream relative to the flow direction of the flows, the two coaxial ducts each being defined between an internal wall and an external wall, upstream of the downstream end of the internal housing, and the secondary flow surrounding the primary flow, characterised in that it consists of disposing at least one divergent radial deflection means in primary duct, spaced apart from the walls of said primary duct.